An air conditioning system that is designed to be retroactively added to, and removed from, an existing aircraft, vehicle, boat or similar confined space. The air conditioning system includes a cooler module that is carried into a first compartment to circulate and cool the air. The cooler module contains a condenser, an evaporator and a compressor. A heat exchanger module is mounted into a vented second compartment. The heat exchanger is capable of exchanging heat with the ambient air. The heat exchanger module is connected to the cooler module with tubes that contain a heat exchanger fluid. In order for the tubes to pass through a compartment barrier, fluid couplings are mounted through the barrier. The tubes connect to the fluid couplings on either side of the barrier. A control unit is provided within the pressurized cabin and/or cockpit for controlling the operations of the cooler module.

A system includes a first fluid flow path configured to condition a pressurized medium and deliver the pressurized medium to one or more loads. The first fluid flow path including an air cycle machine. A second fluid flow path is configured to circulate a working fluid. The second fluid flow path includes a heat exchanger thermally coupled to the first fluid flow path. Within the heat exchanger, heat extracted from the pressurized medium is transferred to the working fluid. The second fluid flow path additionally includes a turbine operably coupled to the air cycle machine, a condenser, and a pump operable to circulate the working fluid through at least a portion of the second fluid flow path. The turbine is rotationally driven by expanding the working fluid across the turbine.

A method, apparatus, system, and computer program product for managing pumps in an aircraft. Flight information about an operation of the pumps in a pump package in the aircraft is received by a computer system. The flight information is received from the aircraft. A number of times that an abnormal switching occurred for the pumps within a window of consecutive flights is determined by the computer system when the abnormal switching is identified from the flight information. A set of actions is performed by the computer system when the abnormal switching occurred a number of times for the pumps within the window of consecutive flights that exceeds a set of thresholds for the abnormal switching that is considered healthy for the pumps.

A power electronics cooling system includes a ram air fan with one or more blades and a ram air fan motor connected via an output shaft. The ram air fan draws in air and passes it across a heat exchanger to cool one or more cooling liquids. One or more pumps pressurize and pump the cooling liquids to various electronic components, including one or more motor controllers. The pumps may be mechanically or electrically coupled to the output shaft of the ram air fan, such that the motor of the ram air fan provides energy to the pumps.

An apparatus is provided for absorbing shocks and a control method capable of protecting cargo from shocks without a separate additional system in a cargo hold of a moving object. The apparatus for absorbing shocks includes at least one inflatable member disposed in a moving object, an air conditioner module installed on the moving object, and a supply pipe connected between the air conditioner module and the inflatable member and providing a refrigerant of the air conditioner module to the inflatable member.

A method for combined cooling and heating in an aircraft, the aircraft including an engine configured to use dihydrogen as fuel, the dihydrogen being stored in liquid form in a tank and being used in gas form in the engine, the dihydrogen being conveyed from the tank to the engine by a main pipe. The method includes the steps of branching off a part of the flow of dihydrogen in a bypass pipe, in parallel with a predefined segment of the main pipe, circulating a first heat transfer fluid in a first closed circuit, carrying out a first heat exchange between the first heat transfer fluid and the dihydrogen circulating in the bypass pipe and carrying out at least one secondary heat exchange. Each secondary heat exchange is carried out between the first heat transfer fluid and a working fluid used in the aircraft which needs to be cooled.

An aircraft includes a cooling compartment and an evaporative chiller configured to cool the cooling compartment. The evaporative chiller includes a compressor, an evaporator having airflow to the cooling compartment, and a condenser. The condenser has an exhaust airflow to cool the condenser. The evaporative chiller has a condensate removal system removing condensate produced by the evaporator using the exhaust airflow of the condenser to discharge the condensate.

Exchanger (16) for cooling hot primary air by means of cold secondary air, comprising: a plurality of channels (80) for the circulation of the secondary air; and a plurality of channels for the circulation of the primary air, characterized in that said exchanger further comprises: water circulation channels (83) each extending adjacently to a secondary channel (80); water-spray micro-perforated hollow bars (63) each extending adjacently to a primary channel (60) and fluidically connected to the micro-perforated hollow bars in order to be able to heat the water by interaction with the primary air before said water is sprayed into the flow of primary air at the inlet of the exchanger.

A power electronics cooling system includes a ram air fan with one or more blades and a ram air fan motor connected via an output shaft. The ram air fan draws in air and passes it across a heat exchanger to cool one or more cooling liquids. One or more pumps pressurize and pump the cooling liquids to various electronic components, including one or more motor controllers. The pumps may be mechanically or electrically coupled to the output shaft of the ram air fan, such that the motor of the ram air fan provides energy to the pumps.

An air-liquid heat exchanger assembly for an environmental control system of an aircraft includes a heat exchanger, a controller, and a bypass valve. The heat exchanger includes a first chamber and a second chamber. The first chamber has a first inlet that is provided a liquid and a first end that is provided air. The second chamber is arranged adjacent the first chamber. The bypass valve is operably coupled to the controller. The bypass valve having an inlet coupled to a first outlet of the first chamber, a first outlet coupled to a second inlet of the second chamber, and a second outlet coupled to a bypass conduit. The controller adjusts a position of the bypass valve to control the flow of liquid through the second chamber and the bypass conduit.